Superplane



J. E. BRoYLEs SUPERPLANE 3 Sheets-Sheet 1 Filed March 25, 1926 fm y, m M mw. www w WNI n M 7, mw .ww s a E \QN.|\M QQ O rw NQ KP %N\ m f M NNQM.\\ bw. h. w R v; NN NN my Q Q H HEME N \0.. m, \\Q Q R, R

Aug 16, 1927' J, E. BRoYLEs SUPERPLANE 3 Shoots-Sheet 2 Filed March 25, 1926 Aug. 16, 1927. E. BYROYLES sUPnnPLANE Filed March 25. 192s 5 Sheets-Sheet 5 Attorney Patented Aug. 16, 1927.

UNITEDv STATES PATENT OFFICE.

J'OHN ENLOE BROYLES, 0F RUSSELLVILLE, MISSOURI, ASSIGNOR OF ONE-HAILIl TO HENRY EMMET ROBERTSON AND THEODORE HENRY WEILER, BOTH VILLE, MISSOURI.

SUPERPLANE.

Application led March 25, 1926. Serial No. 97,277.

The present invention relates generally to improvements in aeroplanes, and aims to provide a superplane of a size much greater than any of those now in use.

A very important object of the invention resides in the shaping of the fuselage or hull, to obtain an aerodynamical lift as the aeroplane is in flight.

Another object of the invention is to provide means for preserving, and also increasing the negative aerodynamical lift.

Another very important object of the invention is to provide means in the fuselage whereby the aerodynamical lift thereof may be decreased when desired.

Another very important object of the invention resides in the combination of a fuselage shaped to provide a maximum aerodynamic lift and having mounted thereon propulsion means which is adjustable to provide a mechanical lift for vertical ascension and descension.

Another very important object of the invention, resides in the combination of an improved fuselage constructed with van aeroplane landing trackway thereon, so that smaller aeroplanes'may land thereon when desired.

Another object of the invention resides in a highly novel buffer landing device to take up the shock when the super-plane lands on the ground` snow or 1ce.

A still further important object of the invention resides in the provision of all of the above features of advantage in an exceedingly simple construction which is strong, durable. easy to maneuver, andv otherwise well adapted to the purpose for which it is designed.

With the above and numerous other objects in view as will appear as the description proceeds. the invention resides 1n certain novel features of construction. and 1n the combination and arrangement of parts as will be hereinafter more fully described and claimed.

In the drawing Figure l is a side elevation of thesuper plane embodying the features ofmy invention. a portion thereof being shown in section.

Fig. 2 is atop plan view thereof,

Fig. 3 is an enlarged fragmentary vertical section taken through one of the front tubes and .buffer landing device,

Flg. 4 is an enlarged detail plan view of one of the central buffers,

Fig. 5 is an enlarged detail transverse section taken substantially on the line 5-5 of Fig. 3, and

Fig. 6 is a vertical detail section taken substantially on the line 66 of Fig. 4.

Referring to the drawing in detail, it will be seen that the fuselage or hull is designated generally by the letter A.. and is substantially rectangular in top plan as is shown in Fig. 2, and in side elevation simulates closely a section through the usual type of plane. The nose of the fuselage has an upwardly and rearwardly disposed curvature as is denoted at. this curvature merging into an elongated downwardly and rearwardly inclination 6 for crea-ting the desirable vacuum thatI provides the negative aerodynamical source of lift. The bottom of the fuselage at its nose inclines downwardly as is indicated at 7 and merges into the concave arcuate curvature 8 for providinfr the positive aerodynamical source of A pair of vertical ins or stabilizers 9 are provided to rise from the top of the fuselageat the sides thereof along the inclination 6 so as to prevent a side inrush of air to destroy the vacuum which provides the negative aerodynamical source of lift.. Vertical rudders 10 are hinged as at 1l to the rear vertical edges of the fins 9. A tube 12 extends from the approximate center of the curvature 8 through the inclination 6 at the approximate center of the vacuum formed thereabove.

In the present instance,` I have shown two of these tubes 12, but it is apparent that the number thereof may` vary as may be desired or found necessary. A valve 13 is hinged as at 14 at the upper end of each tube 12 and may be opened by a cable 15 leading to aA convenient point within the fuselage. By opening the valve 13 it will be seen that both the positive and negative aerodynamical sources of lift may be decreased for the purpose of descension.

In the present example of my superplane. I show three supports 17 at the nose of the fuselage projecting forwardly there from, and four supports 18, two on each side from.

On each support 17, 18, there is mounted a motor frame struct-ure 19 for driving a' propeller20. These motor frames are capable of adjustment about horizontal and vertical axes. The motor frame structure has'been claimed, and disclosed specifically in my ending application, Serial No. 21,876 filed pril 9, 1925. With these motor frames, it is possible for the super-plane to rise vertically and to descend vertically.

At the front and rear of the fuselage A, I provide pontoons 22 which extend from the bottom surface of the fuselage and, of course are`used for landing in water. Particular attention is now directed to Fig. 3, wherein it will be seen that I have disclosed my improved landing device for use in conjunction with the pontoons. lEach pontoon is Vprovided with an exterior longitudinally extending recess 23 on its bottom. Openings 24 are provided in the bottom of the pontoon in registry with the recess 23. Cylinders 25 are mounted interiorly of the pontoon in registry with the opening 24, and are provided with longitudinally extending slots 26. Cylinders 27 are slidable through openings 24 and cylinders 25, and are provided with longitudinally extending slots 28.

A pair of rods 29 rise alongside of each cylinder 25, and have their u per portions threaded as indicated at 30. head 31 extends through the slots 26 and 28 and has apertures 32 for receiving the rods 30. A rod 34 is slidable through a central aperture 35 in the head 31. The cylinders 27 are fixed to runners 37 as is also the rods 34. Nuts 38 are threaded on the rods k29 above lthe head 31. A spring 39 of the helical type is disposed about the rod 34 to impinge against the runner 37 and the head 31. Obviously, by the adjusting of the nuts 38, the tension of this spring may be varied as desired. All three of the buffers shown in Fig. 3 have the same features as just described, however, the center buffer has additional features which will now be referred to in detail.

A frame 4() is disposed in the pontoon about the center cylinder 25 and the top thereof is provided with an opening 41 through which the rod 34 is slidable. A nut 42 is threaded on the rod 34 above the top of the frame 40 and has elongated arms 43 to afford easy adjustment thereof. By screwing this nut 42 on the rod 34, said rod may be lifted, thereby moving the three cylinders 37 inwardly of the pontoon and raising the runner 34 to be housed in the longitudinally extending recess 23 when desired. This would be done, of course, when the super-plane is landed in water, or at other times when it might be desirable.

Attention is now directed particularly to Fig. 2, wherein it will be seen that a portion of the rear end of the fuselage or hull is cut outto provide an opening 45 in which is hinged in any suitable manner suchvas at 46 an elevator 47, the purpose vof operation of which will be guite apparent to those skilled in this art. n the top ofthe fuselage I provide a landing trackway indicated at 48 so that smaller aeroplanes may land onthe super-plane when equipped with the landing mechanisms such as are disclosed in my co-pending application, Serial No. 91,556, filed March 1, 1926.

From the above detailed description, it will be seen that I have provided a superplane having an assembly and construction providing an aerodynamical lifting hull or fuselage having the same outward appearance and relative proportions as the present type of aeroplane wings which obtain the maximum lifting eiiiciency. It is to be understood that the thickness of this type of hull would not be less than six feet and might be of any greater thickness, the other dimensions would be such as to maintain the relative proportions or desirable shape for creating maximum lift. YOf course, I do not wish to be in any way limited in the dimensions. This fuselage, of course, is hollow and affords cabin and storage facilities.

At the front of the fuselage, I mount the laterally extending aeroplane wings 50, preferably three on each side, one above the other, and the same arrangement is provided -at the rear as is indicated at 51. These wings, of course, will be proportioned as will be necessary to obtain the necessary aerodynamical lift. If desired, these wings 50 and 51 may be hingedly mounted in any manner such as is disclosed in my pending application, Serial No. 46,617, filed July 28, 1925, in my improvements in super-airships. In my improvements, I also provide means for aiding in a mechancial manner the lift of the superplane, and for decreasing the aerodynamical lift when desired. I also provide spaces and means for allowing the landing of smaller aeroplanes besides providing an improved type of landing mechanism for this super plane. All of these features of advantage are incorporated in a well balanced manner, affording compactness and convenience and greatly enhancing the maneuverability of the super plane.

The present embodiment of the. invention, in all its features has been disclosed merely by way of example because of the efiiciency and reliability of the structure disclosed in attaining the features of advantage enumerated as desirable in the statement of the invention and the above description. It will be apparent, however, that the numerous changes in the details of construction,

' and. rearwardly and mergin and in the combination andarrangenient of parts may be resorted, to without departing A from the spirit 'or scope of the invention as hereinafter claimed, or without sacrifie'- aving thus described my -invention','what Iclaim as new iszi 1. A super-plane including,.in combination, a fuselage having a 'nose rovided with upwardly and rearwardl inc ined top merging into a downward an rearward inclinatio'n, and a bottom' inclined downwardly into .al concavity, supports. projecting rom the nose inglany of its advantages.

4and sides -of the fuselage, and propeller vmotor mounting on the supports and having vertical and horizontal axes.

,2. A super-plane including, in combination, a fuselage having a nose provided with an upwardly and rearwardly inclined top merging into a downward and rearwardV in-` clination, and` a bottom inclined downwardly and rearwardly and mergingA into a concavity, a support projecting forwardly from the nose and supports projecting from the sides of the fuselage, and propulsion means mounted 'on said supports.

In testimony whereof I aliX my signature.

JoHNpENLoE BRoYLEs. 

